The U.S. Army Ballistic Missile Agency, Redstone Arsenal, Ala., began studies of a large clustered-engine booster to generate 1.5 million pounds of thrust, as one of a related group of space vehicles. During 1957-1958, approximately 50,000 man-hours were expended in this effort.

1957 Dec 10 -

National Integrated Missile and Space Vehicle Development Program

The Army Ballistic Missile Agency completed and forwarded to higher authority the first edition of A National Integrated Missile and Space Vehicle Development Program, which had been in preparation since April 1957. Included was a "short-cut development program" for large payload capabilities, covering the clustered-engine booster of 1.5 million pounds of thrust to be operational in 1963. The total development cost of $850 million during the years 1958-1963 covered 30 research and development flights, some carrying manned and unmanned space payloads. One of six conclusions given in the document was that "Development of the large (1520 K-pounds thrust) booster is considered the key to space exploration and warfare." Later vehicles with greater thrust were also described.

1957 Dec 30 -

Saturn I first proposed.

Von Braun produces 'Proposal for a National Integrated Missile and Space Vehicle Development Plan'. First mention of 1,500,000 lbf booster (Saturn I)

1958 Jul 29 -

Saturn I initial contract.

ARPA gives Von Braun team contract to develop Saturn I (called 'cluster's last stand' due to design concept).

1958 Aug 15 -

Saturn I project initiated by ARPA.

The Advanced Research Projects Agency ARPA provided the Army Ordnance Missile Command (AOMC) with authority and initial funding to develop the Juno V (later named Saturn launch vehicle. ARPA Order 14 described the project: "Initiate a development program to provide a large space vehicle booster of approximately 1.5 million pounds of thrust based on a cluster of available rocket engines. The immediate goal of this program is to demonstrate a full-scale captive dynamic firing by the end of calendar year 1959." Within AOMC, the Juno V project was assigned to the Army Ballistic Missile Agency at Redstone Arsenal Huntsville, Ala.

1958 Sep 1 -

Redstone Arsenal begins Saturn I design studies.

Saturn design studies authorized to proceed at Redstone Arsenal for development of 1.5-million-pound-thrust cluster first stage.

1958 Sep 11 -

Letter contract for the development of the Saturn H-1 rocket engine

A letter contract was signed by NASA with NAA's Rocketdyne Division for the development of the H-1 rocket engine, designed for use in a clustered-engine booster.

1958 Sep 23 -

Juno V project objective changed to multistage carrier vehicle

Following a Memorandum of Agreement between Maj. Gen. John B. Medaris of Army Ordnance Missile Command (AOMC) and Advanced Research Projects Agency (ARPA) Director Roy W. Johnson on this date and a meeting on November 4, ARPA and AOMC representatives agreed to extend the Juno V project. The objective of ARPA Order 14 was changed from booster feasibility demonstration to "the development of a reliable high performance booster to serve as the first stage of a multistage carrier vehicle capable of performing advanced missions."

1958 Oct 11 -

Contract for development of the H-1 engine

Pioneer I, intended as a lunar probe, was launched by a Thor-Able rocket from the Atlantic Missile Range, with the Air Force acting as executive agent to NASA. The 39-pound instrumented payload did not reach escape velocity.

Representatives of Advanced Research Projects Agency, the military services, and NASA met to consider the development of future launch vehicle systems. Agreement was reached on the principle of developing a small number of versatile launch vehicle systems of different thrust capabilities, the reliability of which could be expected to be improved through use by both the military services and NASA.

The Army Ordnance Missile Command (AOMC), the Air Force, and missile contractors presented to the ARPA-NASA Large Booster Review Committee their views on the quickest and surest way for the United States to attain large booster capability. The Committee decided that the Juno V approach advocated by AOMC was best and NASA started plans to utilize the Juno V booster.

1959 Jan 27 -

NASA National Space Vehicle Program

After consultation and discussion with DOD, NASA formulated a national space vehicle program. The central idea of the program was that a single launch vehicle should be developed for use in each series of future space missions. The launch vehicle would thus achieve a high degree of reliability, while the guidance and payload could be varied according to purpose of the mission. Four general-purpose launch vehicles were described: Vega, Centaur, Saturn, and Nova. The Nova booster stage would be powered by a cluster of four F-1 engines, the second stage by a single F-1, and the third stage would be the size of an intercontinental ballistic missile but would use liquid hydrogen as a fuel. This launch vehicle would be the first in a series that could transport a man to the lunar surface and return him safely to earth in a direct ascent mission. Four additional stages would be required in such a mission.

1959 Feb 2 -

Booster name changed from Juno V to Saturn

The Army proposed that the name of the large clustered-engine booster be changed from Juno V to Saturn, since Saturn was the next planet after Jupiter. Roy W. Johnson, Director of the Advanced Research Projects Agency, approved the name on February 3.

1959 Feb 4 -

Early agreement required on Saturn upper stages

Maj. Gen. John B. Medaris of the Army Ordnance Missile Command (AOMC) and Roy W. Johnson of the Advanced Research Projects Agency (ARPA) discussed the urgency of early agreement between ARPA and NASA on the configuration of the Saturn upper stages. Several discussions between ARPA and NASA had been held on this subject. Johnson expected to reach agreement with NASA the following week. He agreed that AOMC would participate in the overall upper stage planning to ensure compatibility of the booster and upper stages.

1959 Feb 15 -

NASA Booster Development Plan for 60's

NASA issues plan for development in next decade of Vega (later cancelled as too similar to Agena), Centaur, Saturn, and Nova launch vehicles. Juno V renamed Saturn I.

The Army Ordnance Missile Command submitted to NASA a report entitled "Preliminary Study of an Unmanned Lunar Soft Landing Vehicle," recommending the use of the Saturn booster.

1959 May 3 -

First H-1 engine for the Saturn delivered

The first Rocketdyne H-1 engine for the Saturn arrived at the Army Ballistic Missile Agency (ABMA ). The H-1 engine was installed in the ABMA test stand on May 7, first test-fired on May 21, and fired for 80 seconds on May 29. The first long-duration firing - 151.03 seconds - was on June 2.

NASA authorized $150,000 for Army Ordnance Missile Command studies of a lunar exploration program based on Saturn-boosted systems. To be included were circumlunar vehicles, unmanned and manned; close lunar orbiters; hard lunar impacts; and soft lunar landings with stationary or roving payloads.

1959 Oct 21 -

Transfer to NASA of the Army Ballistic Missile Agency's Development Operations Division

After a meeting with officials concerned with the missile and space program, President Dwight D. Eisenhower announced that he intended to transfer to NASA control the Army Ballistic Missile Agency's Development Operations Division personnel and facilities. The transfer, subject to congressional approval, would include the Saturn development program.

1959 Nov 2 -

Transfer of Saturn I project to NASA announced.

President Eisenhower announced his intention of transferring the Saturn project to NASA, which became effective on March 15, 1960.

1959 Dec 6 -

Plan for transferring the Army Ballistic Missile Agency and Saturn to NASA

The initial plan for transferring the Army Ballistic Missile Agency and Saturn to NASA was drafted. It was submitted to President Dwight D. Eisenhower on December 1 1 and was signed by Secretary of the Army Wilber M. Brucker and Secretary of the Air Force James H. Douglas on December 16 and by NASA Administrator T. Keith Glennan on December 17.

1959 Dec 7 -

Engineering and cost study for a new Saturn configuration

The Advanced Research Projects Agency ARPA and NASA requested the Army Ordnance Missile Command AOMC to prepare an engineering and cost study for a new Saturn configuration with a second stage of four 20,000-pound-thrust liquid-hydrogen and liquid-oxygen engines (later called the S-IV stage) and a modified Centaur third stage using two of these engines later designated the S-V stage).
Additional Details: Engineering and cost study for a new Saturn configuration.

The Army Ballistic Missile Agency's Development Operations Division and the Saturn program were transferred to NASA after the expiration of the 60-day limit for congressional action on the President's proposal of January 14. (The President's decision had been made on October 21, 1959.) By Executive Order, the President named the facilities the "George C. Marshall Space Flight Center." Formal transfer took place on July 1.

STG's Robert O. Piland, during briefings at NASA Centers, presented a detailed description of the guidelines for missions, propulsion, and flight time in the advanced manned spacecraft program:

The spacecraft should be capable ultimately of manned circumlunar reconnaissance. As a logical intermediate step toward future goals of lunar and planetary landing many of the problems associated with manned circumlunar flight would need to be solved.

The lunar spacecraft should be capable of earth orbit missions for initial evaluation and training. The reentry component of this spacecraft should be capable of missions in conjunction with space laboratories or space stations. To accomplish lunar reconnaissance before a manned landing, it would be desirable to approach the moon closer than several thousand miles. Fifty miles appeared to be a reasonable first target for study purposes.

The spacecraft should be designed to be compatible with the Saturn C-1 or C-2 boosters for the lunar mission. The multiman advanced spacecraft should not weigh more than 15,000 pounds including auxiliary propulsion and attaching structure.

A flight-time capability of the spacecraft for 14 days without resupply should be possible. Considerable study of storage batteries, fuel cells, auxiliary power units, and solar batteries would be necessary. Items considered included the percentage of the power units to be placed in the "caboose" (space laboratory), preference for the use of storage batteries for both power and radiation shielding, and redundancy for reliability by using two different types of systems versus two of the same system.

- 1960 April 1-May 3 -

Guidelines for an advanced manned spacecraft program presented by STG Spacecraft: Apollo CSM.

Members of STG presented guidelines for an advanced manned spacecraft program to NASA Centers to enlist research assistance in formulating spacecraft and mission design.

To open these discussions, Director Robert R. Gilruth summarized the guidelines: manned lunar reconnaissance with a lunar mission module, corollary earth orbital missions with a lunar mission module and with a space laboratory, compatibility with the Saturn C-1 or C-2 boosters (weight not to exceed 15,000 pounds for a complete lunar spacecraft and 25,000 pounds for an earth orbiting spacecraft), 14-day flight time, safe recovery from aborts, ground and water landing and avoidance of local hazards, point (ten square-mile) landing, 72-hour postlanding survival period, auxiliary propulsion for maneuvering in space, a "shirtsleeve" environment, a three-man crew, radiation protection, primary command of mission on board, and expanded communications and tracking facilities. In addition, a tentative time schedule was included, projecting multiman earth orbit qualification flights beginning near the end of the first quarter of calendar year 1966.

1960 Apr 6 -

Four H-1's fired together.

Four of the eight H-1 engines of the Saturn C-1 first-stage booster were successfully static-fired at Redstone Arsenal for seven seconds.

1960 Apr 26 -

Douglas to build the second stage (S-IV) of the Saturn C-1

NASA announced the selection of the Douglas Aircraft Company to build the second stage (S-IV) of the Saturn C-1 launch vehicle.

1960 Apr 29 -

All eight H-1 engines of the Saturn C-1 first stage ground-tested simultaneously

At Redstone Arsenal, all eight H-1 engines of the first stage of the Saturn C-1 launch vehicle were static-fired simultaneously for the first time and achieved 1.3 million pounds of thrust.

1960 May 26 -

Assembly of the first Saturn flight booster began

Assembly of the first Saturn flight booster, SA-1, began at Marshall Space Flight Center.

1960 May 26 -

First public demonstration of the H-1 engine

Eight H-1 engines of the first stage of the Saturn C-1 launch vehicle were static-fired for 35.16 seconds, producing 1.3 million pounds of thrust. This first public demonstration of the H-1 took place at Marshall Space Flight Center.

The Saturn C-1 first stage successfully completed its first series of static tests at the Marshall Space Flight Center with a 122-second firing of all eight H-1 engines.

1960 Sep 30 -

Space Exploration Program Council

The fourth meeting of the Space Exploration Program Council was held at NASA Headquarters. The results of a study on Saturn development and utilization was presented by the Ad Hoc Saturn Study Committee. Objectives of the study were to determine (1) if and when the Saturn C-2 launch vehicle should be developed and (2) if mission and spacecraft planning was consistent with the Saturn vehicle development schedule. No change in the NASA Fiscal Year 1962 budget was contemplated. The Committee recommended that the Saturn C-2 development should proceed on schedule (S-II stage contract in Fiscal Year 1962, first flight in 1965). The C-2 would be essential, the study reported, for Apollo manned circumlunar missions, lunar unmanned exploration, Mars and Venus orbiters and capsule landers, probes to other planets and out-of- ecliptic, and for orbital starting of nuclear upper stages.
Additional Details: Space Exploration Program Council.

1960 Dec 2 -

Saturn I static firing.

First of new series of static firings of Saturn considered only 50 percent successful in 2-second test at MSFC.

Palaemon, a 180-foot barge built to transport the Saturn launch vehicle from MSFC to Cape Canaveral by water, was formally accepted by MSFC Director from Maj. Gen. Frank S. Besson, Chief of Army Transportation.

1961 Jan 26 -

Saturn C-1 changed to a two-stage configuration

Wernher von Braun, Director of Marshall Space Flight Center, proposed that the Saturn C-1 launch vehicle be changed from a three-stage to a two-stage configuration to meet Apollo program schedules. The planned third stage (S-V) would be dropped.

- 1961 January -

Saturn first stage recovery system study

Marshall Space Flight Center awarded contracts to NAA and Ryan Aeronautical Corporation to investigate the feasibility of recovering the first stage (S-I) of the Saturn launch vehicle by using a Rogallo wing paraglider.

Elimination of third-stage development, since two stages could put more than ten tons into earth orbit.

Use of six LR-115 (15,000-pound) Centaur engines (second-stage thrust thus increased from 70,000 to 90,000 pounds).

Redesign of the first stage (S-1) to offer more safety for manned missions.

Plans were also presented to accelerate the development of the Saturn C- 2, and a recommendation was made that a prime contractor be selected to work on the second stage (S-II) of the C-2. NASA Headquarters approved the C-2 plans on March 31.

Final NASA report on the study proposed for Saturn for use as Dyna-Soar booster was presented to the Air Force.

1961 Apr 29 -

Saturn I fight qualification.

The first successful flight qualification test of the Saturn SA-1 booster took place in an eight-engine test lasting 30 seconds.

- 1961 April -

Air transport of the Saturn C-1 second stage feasible

The Douglas Aircraft Company reported that air transport of the Saturn C-1 second stage (S-IV) was feasible.

1961 May 8 -

S-IV satisfactory for Apollo missions

After study and discussion by STG and Marshal! Space Flight Center officials, STG concluded that the current 154-inch diameter of the second stage (S-IV) adapter for the Apollo spacecraft would be satisfactory for the Apollo missions on Saturn flights SA-7, SA-8, SA-9, and SA-10.

1961 Jun 1 -

Change in the Saturn C-1 configuration

NASA announced a change in the Saturn C-1 vehicle configuration. The first ten research and development flights would have two stages, instead of three, because of the changed second stage (S-IV) and, starting with the seventh flight vehicle, increased propellant capacity in the first stage (S-1) booster.

Collapse of a lock in the Wheeler Dam below Huntsville on the Tennessee River interdicted the planned water route of the first Saturn space booster from Marshall Space Flight Center to Cape Canaveral on the barge Palaemon.

Huge Saturn launch complex at Cape Canaveral dedicated in brief ceremony by NASA, construction of which was supervised by the Army Corps of Engineers. Giant gantry, weighing 2,800 tons and being 310 feet high, is largest movable land structure in North America.

1961 Jun 23 -

NASA / DOD agree to define support requirements

NASA Associate Administrator Robert C. Seamans, Jr., requested Kurt H. Debus, Director of the NASA Launch Operations Directorate, and Maj. Gen. Leighton I. Davis, Commander of the Air Force Missile Test Center, to make a joint analysis of all major factors regarding the launch requirements, methods, and procedures needed in support of an early manned lunar landing. The schedules and early requirements were to be considered in two phases:

in line with the Fleming Report, a direct flight to the moon would be assumed, using the Saturn C-1 and C-3 launch vehicles in early support phases and liquid- or solid-fueled Nova launch vehicles for the lunar landing;

as a possible alternative or parallel program, orbital rendezvous operations using Saturn C-3 and liquid-fueled Nova.

The analysis should include recommendations on mutual NASA-DOD range responsibilities, authority, management structures, and other allied subjects. On June 30, Seamans notified Debus and Davis that the evaluation of tracking and command stations should not be included in the study. He stressed that the factors of immediate concern with regard to launch operations were those of launch site locations, land acquisition requirements, spacecraft and launch vehicle preparation facilities, vehicle launch facilities, and other facilities and requirements at the launch site. (Phase I of the Report was submitted on July 31.)

1961 Jun 23 -

Saturn C-1 to be operational in 1964

NASA announced that the Saturn C-1 launch vehicle, which could place ten-ton payloads in earth orbit, would be operational in 1964.

Navy barge Compromise, carrying first Saturn booster, stuck in the mud in the Indian River just south of Cape Canaveral. Released several hours later, the Saturn was delayed only 24 hours in its 2,200-mile journey from Huntsville.

1961 Oct 20 -

STG discussed development of automatic checkout system for the entire NASA launch vehicle program

The MSFC-STG Advanced Program Coordination Board met at STG and discussed the question of the development of an automatic checkout system which would include the entire launch vehicle program from the Saturn C-1 through the Nova. It agreed that the Apollo contractor should be instructed to make the spacecraft electrical subsystems compatible with the Saturn complex.

In further discussion, Paul J. DeFries of Marshall Space Flight Center MSFC presented a list of proposed guidelines for use in studying early manned lunar landing missions:

The crew should draw on its own resources only when absolutely necessary. Equipment and service personnel external to the spacecraft should be used as much as possible.

Early lunar expeditions would receive active external support only up to the time of the launch from earth orbit.

The crew would board the spacecraft only after it was checked out and ready for final countdown and launch.

The first Apollo crews should have an emergency shelter available on the moon which could afford several months of lift: support and protection.

The capability for clocking an orbital launch vehicle with a propulsion stage - the "connecting mode" - should be possible.

The capability of fueling an orbital launch vehicle should be made available - "fueling mode."

The capability of making repairs, replacements, or adjustments in orbit should be developed.

For repairs, replacements, and adjustments on the orbital launch vehicle in earth orbit, two support vehicles would be necessary. These would be a Saturn C-1 launch vehicle manned by Apollo technicians and an unmanned Atlas-Centaur launch vehicle carrying repair kits.

Development of docking, testing of components, and techniques for docking and training of man in orbital operations could be carried out by a space ferry loaded with a Mercury capsule.

Some of the points discussed in connection with these suggestions were:

Orbital launch operations were just as complex, if not more complex, than earth-launched operations.

A question existed as to how complex the orbital launch facility could be and what its function should be.

There was a possibility that the crew could do most of the checkout and launch operations. Studies should be made to define the role of the crew versus the role of a proposed MSFC auxiliary checkout and maintenance crew.

After the discussion on orbital launch operations, the Board agreed that contemporary technology was inadequate to support such operations. Both STG and MSFC would need to study and develop both refueling and connector techniques.

Largest known rocket launch to date, the Saturn I 1st stage booster, successful on first test flight from Atlantic Missile Range. With its eight clustered engines developing almost 1.3 million pounds of thrust at launch, the Saturn (SA-1) hurled waterfilled dummy upper stages to an altitude of 84.8 miles and 214.7 miles down range. In a postlaunch statement, Administrator Webb said: "The flight today was a splendid demonstration of the strength of our national space program and an important milestone in the buildup of our national capacity to launch heavy payloads necessary to carry out the program projected by President Kennedy on May 25.".

1961 Nov 17 -

Contract issued for build of 20 Saturn I's.

NASA announced that the Chrysler Corporation had been chosen to build 20 Saturn first-stage (S-1) boosters similar to the one tested successfully on October 27 . They would be constructed at the Michoud facility near New Orleans, La. The contract, worth about $200 million, would run through 1966, with delivery of the first booster scheduled for early 1964.

1961 Dec 8 -

Support service contractor selected for Michoud.

NASA selected Mason-Rust as the contractor to provide support services at NASA's Michoud plant near New Orleans, providing housekeeping services through June 30, 1962 for the three contractors who would produce the Saturn S-I and S-IB boosters and the Rift nuclear upper-stage vehicle.

A meeting on the technical aspects of earth orbit rendezvous was held at NASA Headquarters. Representatives from various NASA offices attended: Arthur L. Rudolph, Paul J. DeFries, Fred L. Digesu, Ludie G. Richard, John W. Hardin, Jr., Ernst D. Geissler, and Wilson B. Schramm of Marshall Space Flight Center (MSFC); James T. Rose of MSC; Friedrich O. Vonbun, Joseph W. Siry, and James J. Donegan of Goddard Space Flight Center (GSFC); Douglas R. Lord, James E. O'Neill, Richard J. Hayes, Warren J. North, and Daniel D. McKee of the NASA Office of Manned Space Flight (OMSF). Joseph F. Shea, Deputy Director for Systems, OMSF, who had called the meeting, defined in general terms the goal of the meeting: to achieve agreement on the approach to be used in developing the earth orbit rendezvous technique. After two days of discussions and presentations, the Group approved conclusions and recommendations:

Gemini rendezvous operations could and must provide substantial experience with rendezvous techniques pertinent to Apollo.

Incorporation of the Saturn guidance equipment in a scaled-down docking module for the Agenas in the Gemini program was not required.

Complete development of the technique and equipment for Apollo rendezvous and docking should be required before the availability of the Saturn C-5 launch vehicle.

Full-scale docking equipment could profitably be developed by three- dimensional ground simulations. MSFC would prepare an outline of such a program.

The Apollo rendezvous technique and actual hardware could be flight- tested with the Saturn C-1 launch vehicle. MSFC would prepare a proposed flight test program.

The choice of connecting or tanking modes must be made in the near future. The MSFC Orbital Operations Study program should be used to provide data to make this decision.

The rendezvous technique which evolved from this meeting would place heavy requirements on the ground tracking network. GSFC should provide data relating the impact of detailed trajectory considerations to ground tracking station requirements.

(This meeting was part of a continuing effort to select the lunar mission mode.)

1962 Feb 27 -

Manned Space Flight Management Council meeting

The preparation of schedules based on the NASA Fiscal Year 1962 budget (including the proposed supplemental appropriation), the Fiscal Year 1963 budget as submitted to Congress, and Fiscal Year 1964 and subsequent funding was discussed at the Manned Space Flight Management Council meeting. Program assumptions as presented by Wernher von Braun, Director, Marshall Space Flight Center (MSFC), were approved for use in preparation of the schedules :

The Saturn C-5 launch vehicle and earth orbital rendezvous were considered the primary mode for the lunar landing.

Full-scale orbit operations development, including ground testing, would be accomplished, using S-I boosters and orbital upper stages. This development would be planned so that upper stages and rendezvous techniques would be developed by the time the C-5 was operational. Planning would consider both connecting and fueling modes.

The development of a two-stage Nova with liquid-propellant engines in both stages would be activated as early as realistically feasible. This would provide an alternative, direct flight mode carrying the same orbital launch vehicle as developed for the C-5.

There would be no solid-propellant vehicle development.

Charles W. Frick of MSC and Hans H. Maus of MSFC would coordinate schedule assumptions between the Centers.

A small group within the MSC Apollo Spacecraft Project Office developed a preliminary program schedule for three approaches to the lunar landing mission: earth orbit rendezvous, direct ascent, and lunar orbit rendezvous. The exercise established a number of ground rules :

Establish realistic schedules that would "second guess" failures but provide for exploitation of early success.

Complete the flight development of spacecraft modules and operational techniques, using the Saturn C-1 and C-1B launch vehicles, prior to the time at which a "man-rated" C-5 launch vehicle would become available.

Develop the spacecraft operational techniques in "buildup" missions that would progress generally from the simple to the complex.

Use the spacecraft crew at the earliest time and to the maximum extent, commensurate with safety considerations, in the development of the spacecraft and its subsystems.

The exercise also provided a basis for proceeding with the development of definitive schedules and a program plan.

Second suborbital test of Saturn I. The Saturn SA-2 first stage booster was launched successfully from Cape Canaveral. The rocket was blown up intentionally and on schedule about 2.5 minutes after liftoff at an altitude of 65 miles, dumping the water ballast from the dummy second and third stages into the upper atmosphere. The experiment, Project Highwater, produced a massive ice cloud and lightning-like effects. The eight clustered H-1 engines in the first stage produced 1.3 million pounds of thrust and the maximum speed attained by the booster was 3,750 miles per hour. Modifications to decrease the slight fuel sloshing encountered near the end of the previous flight test were successful.

1962 Jun 22 -

Selection of ablative material for Apollo heatshield

MSC Director Robert R. Gilruth reported to the Manned Space Flight Management Council that the selection of the ablative material for the Apollo spacecraft heatshield would be made by September 1. The leading contender for the forebody ablative material was an epoxy resin with silica fibers for improving char strength and phenolic microballoons for reducing density.

In addition, Gilruth noted that a reevaluation of the Saturn C-1 and C-1B launch capabilities appeared to indicate that neither vehicle would be able to test the complete Apollo spacecraft configuration, including the lunar excursion module. Complete spacecraft qualification would require the use of the Saturn C-5.

1962 Aug 16 -

S-IV successfully static-fired for the first time

The second stage (S-IV) of the Saturn C-1 launch vehicle was successfully static-fired for the first time in a ten-second test at the Sacramento, Calif., facility by the Douglas Aircraft Company.

Third suborbital test of Saturn I. Saturn-Apollo 3 (Saturn C-1, later called Saturn I) was launched from the Atlantic Missile Range. Upper stages of the launch vehicle were filled with 23000 gallons of water to simulate the weight of live stages. At its peak altitude of 167 kilometers (104 miles), four minutes 53 seconds after launch, the rocket was detonated by explosives upon command from earth. The water was released into the ionosphere, forming a massive cloud of ice particles several miles in diameter. By this experiment, known as "Project Highwater," scientists had hoped to obtain data on atmospheric physics, but poor telemetry made the results questionable. The flight was the third straight success for the Saturn C-1 and the first with maximum fuel on board.

1963 Jan 10 -

Unmanned Apollo spacecraft to be flown on Saturn C-1

MSC and OMSF agreed that an unmanned Apollo spacecraft must be flown on the Saturn C-1 before a manned flight. SA-10 was scheduled to be the unmanned flight and SA-111, the first manned mission.

1963 Feb 7 -

Simplified terminology for the Saturn booster series

NASA announced a simplified terminology for the Saturn booster series: Saturn C-1 became "Saturn I," Saturn C-1B became "Saturn IB," and Saturn C-5 became "Saturn V."

1963 Feb 20 -

Saturn engine-out capability investigated

At a meeting of the MSC-MSFC Flight Mechanics Panel, it was agreed that Marshall would investigate "engine-out" capability (i.e., the vehicle's performance should one of its engines fail) for use in abort studies or alternative missions. Not all Saturn I, IB, and V missions included this engine-out capability. Also, the panel decided that the launch escape system would be jettisoned ten seconds after S-IV ignition on Saturn I launch vehicles.

North American completed construction of Apollo boilerplate (BP) 9, consisting of launch escape tower and CSM. It was delivered to MSC on March 18, where dynamic testing on the vehicle began two days later. On April 8, BP-9 was sent to MSFC for compatibility tests with the Saturn I launch vehicle.

1963 Mar 13 -

First long-duration static test of Saturn SA-5 first stage

The first stage of the Saturn SA-5 launch vehicle was static fired at MSFC for 144.44 seconds in the first long-duration test for a Block II S-1. The cluster of eight H-1 engines produced 680 thousand kilograms (1.5 million pounds) of thrust. An analysis disclosed anomalies in the propulsion system. In a final qualification test two weeks later, when the engines were fired for 143.47 seconds, the propulsion problems had been corrected.

Fourth suborbital test of Saturn I. The S-I Saturn stage reached an altitude of 129 kilometers (80 statute miles) and a peak velocity of 5,906 kilometers (3,660 miles) per hour. This was the last of four successful tests for the first stage of the Saturn I vehicle. After 100 seconds of flight, No. 5 of the booster's eight engines was cut off by a preset timer. That engine's propellants were rerouted to the remaining seven, which continued to burn. This experiment confirmed the "engine-out" capability that MSFC engineers had designed into the Saturn I.

1963 Aug 5 -

First static firing test of Saturn S-IV stage for SA-5

In what was to have been an acceptance test, the Douglas Aircraft Company static fired the first Saturn S-IV flight stage at Sacramento, Calif. An indication of fire in the engine area forced technicians to shut down the stage after little more than one minute's firing. A week later the acceptance test was repeated, this time without incident, when the vehicle was fired for over seven minutes. (The stage became part of the SA-5 launch vehicle, the first complete Saturn I to fly.)

1963 Sep 16 -

Apollo launch escape system modified

The launch escape system was modified so that, under normal flight conditions, the crew could jettison the tower. On unmanned Saturn I flights, tower jettison was initiated by a signal from the instrument unit of the S-IV (second) stage.

1963 Nov 15 -

An engine hard-over maximum q manual abort was impractical for the Apollo CSM on Saturn I and IB

NASA and contractor studies showed that, in the event of an engine hard-over failure during maximum q, a manual abort was impractical for the Saturn I and IB, and must be carried out by automatic devices. Studies were continuing to determine whether, in a similar situation, a manual abort was possible from a Saturn V.

First first mission of Block II Saturn with two live stages. SA-5, a vehicle development flight, was launched from Cape Kennedy Complex 37B at 11:25:01.41, e.s.t. This was the first flight of the Saturn I Block II configuration (i.e., lengthened fuel tanks in the S-1 and stabilizing tail fins), as well as the first flight of a live (powered) S-IV upper stage. The S-1, powered by eight H-1 engines, reached a full thrust of over 680,400 kilograms (1.5 million pounds) the first time in flight. The S-IV's 41,000 kilogram (90,000-pound-thrust cluster of six liquid-hydrogen RL-10 engines performed as expected. The Block II SA-5 was also the first flight test of the Saturn I guidance system.

A Saturn I vehicle SA-9 launched a multiple payload into a high 744 by 496 km (462 by 308 mi) earth orbit. The rocket carried a boilerplate (BP) CSM (BP-16) and, fitted inside the SM, the Pegasus I meteoroid detection satellite. This was the eighth successful Saturn flight in a row, and the first to carry an active payload. BP-16's launch escape tower was jettisoned following second-stage S-IV ignition. After attaining orbit, the spacecraft were separated from the S-IV. Thereupon the Pegasus I's panels were deployed and were ready to perform their task, i.e., registering meteoroid impact and relaying the information to the ground.

Chrysler contract for support services for the Saturn I and IB launch programs modified

KSC supplemented Chrysler Corporation's contract for support services for the Saturn I and IB launch programs. Effective through June 30, 1968, the agreement would cost NASA $41 million plus an award fee.

MSC requested that Grumman incorporate in the command list for LEMs 1, 2, and 3 the capability for turning the LEM transponder off and on by real-time radio command from the Manned Space Flight Network. Necessity for capability of radio command for turning the LEM transponder on after LEM separation resulted from ASPO's decision that the LEM and Saturn instrument unit S-band transponders would use the same transmission and reception frequencies.

Pegasus 2 was a meteoroid detection satellite. The Saturn I launch vehicle (SA-8) placed the spacecraft, protected by a boilerplate CSM (BP-26), into a 740-by-509-km (460-by-316-mi) orbit. Once in orbit, the dummy CSM was jettisoned. Pegasus 2, still attached to the second stage of the launch vehicle, then deployed its 29-m (96-ft) winglike panels. Within several hours, the device began registering meteoroid hits.

NASA launched Pegasus 3, third of the meteoroid detection satellites, as scheduled at 8:00 a.m. EST, from Cape Kennedy. As earlier, an Apollo spacecraft (boilerplate 9) served as the payload's shroud. This flight (SA-10) marked the end of the Saturn I program, which during its seven-year lifetime had achieved 10 straight successful launches and had contributed immeasurably to American rocket technology.

NASA signed a supplemental agreement with Chrysler Corp.'s Space Division at New Orleans, La., converting the uprated Saturn I first-stage production contract from cost-plus-fixed-fee to cost-plus-incentive-fee. Under the agreement, valued at $339 million, the amount of the contractor's fee would be based on ability to perform assigned tasks satisfactorily and meet prescribed costs and schedules. The contract called for Chrysler to manufacture, assemble and test 12 uprated Saturn I first stages and provide system engineering, integration support, ground support equipment, and launch services.

1966 Oct 19 -

AS-204, first Apollo manned flight announced

Apollo-Saturn 204 was to be the first manned Apollo mission, NASA announced through the manned space flight Centers. The news release, prepared at NASA Hq., said the decision had been made following a Design Certification Review Board meeting held the previous week at OMSF. The launch date had not been determined. Crewmen for the flight would be Virgil I. Grissom, command pilot; Edward H. White II, senior pilot; and Roger B. Chaffee, pilot. The backup crew would be James A. McDivitt, command pilot; David R. Scott, senior pilot; and Russell L. Schweickart, pilot. The AS-204 spacecraft would be launched by an uprated Saturn I launch vehicle on its earth-orbital mission "to demonstrate spacecraft and crew operations and evaluate spacecraft hardware performance in earth orbit."